CN110907186A - Rotor vibration phase measuring and calculating method for aeroengine test bed - Google Patents
Rotor vibration phase measuring and calculating method for aeroengine test bed Download PDFInfo
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- CN110907186A CN110907186A CN201911089407.5A CN201911089407A CN110907186A CN 110907186 A CN110907186 A CN 110907186A CN 201911089407 A CN201911089407 A CN 201911089407A CN 110907186 A CN110907186 A CN 110907186A
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/04—Testing internal-combustion engines
- G01M15/12—Testing internal-combustion engines by monitoring vibrations
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- G01—MEASURING; TESTING
- G01H—MEASUREMENT OF MECHANICAL VIBRATIONS OR ULTRASONIC, SONIC OR INFRASONIC WAVES
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Abstract
The invention belongs to the technical field of aeroengine fault monitoring, and particularly relates to a rotor vibration phase measuring and calculating method for an aeroengine test bed. The method of the invention utilizes the central bevel gear pair and the accessory gearbox which have direct and definite transmission relation with the internal rotor of the engine on the premise of not damaging and changing the structure of the aircraft engine, designs the inverter gearbox and installs the inverter gearbox at the plug hole of the rocking handle, enables the output gear shaft of the inverter gearbox to be consistent with the rotation state of the internal rotor of the engine through the spline shaft of the rocking handle, and measures the vibration phase on the output gear shaft of the inverter gearbox, thereby realizing the extraction of the vibration phase of the rotor.
Description
Technical Field
The invention belongs to the technical field of aeroengine fault monitoring, and particularly relates to a rotor vibration phase measuring and calculating method for an aeroengine test bed.
Background
With the continuous development of the research and development technology of the aero-engine, the application of the engine is more and more extensive, in order to ensure the flight safety of the airplane, the research on the vibration monitoring and diagnosis technology of the aero-engine becomes a more concerned hot spot, and the improvement of the maintenance efficiency of the aero-engine also becomes a problem to be solved at present.
Particularly, in the technical field of vibration monitoring and diagnosis of aircraft engines, a power frequency vibration reference phase (hereinafter referred to as a vibration phase) of a rotor can provide an important basis for analyzing and diagnosing faults of the rotor of the aircraft engine. However, most of the prior aircraft engines do not consider the requirement of measuring the vibration phase of the rotor during design, and the structure of the rotor-casing inside the engine is complex and compact, as shown in fig. 1, the rotor works in a high-temperature and high-pressure environment, and in order to ensure uniform flow field, the bypass of the engine does not allow foreign matters, and the condition of directly mounting an eddy current sensor or a photoelectric sensor is not provided, so that the phase of the rotor vibration cannot be measured.
Disclosure of Invention
In view of the above, the present invention provides a rotor vibration phase measurement and calculation method for an aircraft engine test bed, which utilizes a central bevel gear pair and an accessory gearbox that have a direct and definite transmission relationship with an internal rotor of an engine on the premise of not damaging and changing the structure of the aircraft engine, designs an inverter gearbox and installs the inverter gearbox at a rocking handle socket, enables an output gear shaft of the inverter gearbox to be consistent with the rotation state of the internal rotor of the engine through a rocking handle spline shaft, and measures a vibration phase on the output gear shaft of the inverter gearbox, thereby realizing extraction of the rotor vibration phase.
The purpose of the invention is realized by the following technical scheme.
A rotor vibration phase measuring and calculating method for an aircraft engine test bed comprises the following steps:
(1) designing and processing inverter gear box
A rotor within the aircraft engine typically drives the fuel pump, the lube pump, the speed sensor, and the crank spline shaft through a pair of central bevel gears and a gear train in the accessory case gearbox; similarly, the rotor can be turned by a gear train driven by a rocking handle spline shaft on the accessory case gear box in a reverse direction. Under the premise of not changing the accurate transmission ratio of a transmission gear train between a rotor inside the aircraft engine and a corresponding rocking handle spline shaft, carrying out equivalent reverse reduction on the transmission gear train between the rotor and the rocking handle spline shaft, wherein the reduced number of pairs of gears is the number of pairs of gears in the reverse gearbox;
the inversion gearbox comprises a box body, an input gear shaft, an output gear shaft, more than one transmission gear shaft, a rolling bearing and a spline housing, wherein the rolling bearing is respectively matched with the input gear shaft, the more than one transmission gear shaft and the output gear shaft;
(2) mounting contravariant gear box
The inverter gearbox is installed on the test bed through the installation assembly, and the spline sleeve is meshed with a rocking handle spline shaft on the accessory casing gearbox;
the requirements of the mounting assembly are as follows: on one hand, good axial restraint is provided for the inverter gear box, the axial movement of the inverter gear box is effectively limited, on the other hand, the position of the inverter gear box can be adjusted and fixed in two directions which are parallel to and vertical to the horizontal radius of the engine, and a good centering state is provided for the assembly between the input gear shaft and the rocking handle spline shaft; wherein the axial direction is consistent with the axial direction of the input gear shaft;
(3) build lubricating system of contravariant gear box
Selecting lubricating oil with an applicable model according to the actual operating rotating speed range of an engine rotor, combining a pump, an oil tank, a pipeline, a heat exchanger and a throttle valve according to the actual condition of a test bed, and connecting a lubricating oil inlet and a lubricating oil outlet on an inverter gear box, wherein a lubricating system of the inverter gear box is built to lubricate and cool a gear and a rolling bearing assembly, so that the parts are prevented from being damaged by serious abrasion, gluing and the like;
(4) rotor vibration phase measurement
Making a physical mark capable of triggering level conversion of the sensor on an output gear shaft of the inverter gearbox, and taking the physical mark as a '0 phase' reference point of rotor vibration to enable the sensor to be in a triggered state, and meanwhile, installing a vibration sensor on the outer surface of a rotor casing; keeping the rotor in a static state, enabling a hole detector to penetrate through a hole detecting hole in a rotor casing, and recording the number of the blade on the blade disc corresponding to the hole detecting hole (the number of the blade is marked in sequence from 1, and the marking sequence of the number of the blade is consistent with the rotation direction of the rotor); then, when the test bed runs, synchronously acquiring a vibration signal and a key phase signal, calculating a vibration phase which is not on a unified reference according to the acquired signal, and then converting according to the following formula to obtain a vibration phase of the rotor relative to the unified reference (taking the vibration phase of the initial position of the No. 1 blade on the stage blade disc corresponding to the hole probing hole as a reference);
in the formula, F is a vibration phase relative to a uniform reference, F' is a vibration phase without a uniform reference, N is a blade number on a blade disc corresponding to a hole probing hole, and Z is the total number of blades of the blade disc corresponding to the hole probing hole.
Further, the mounting assembly in the step (2) comprises a horizontal support plate, a vertical support plate, an axial pressure plate, a radial pressure plate and a U-shaped radial support plate; the upper side surface of the vertical supporting plate is an inclined surface, and long through holes are respectively processed on the end surface of the closed end of the U-shaped radial supporting plate and the lower side surface of the vertical supporting plate;
the end face of the closed end of the U-shaped radial supporting plate is connected with the upper side face of the vertical supporting plate, the axial pressing plate is perpendicular to the upper side face of the vertical supporting plate and is connected with the U-shaped radial supporting plate, the radial pressing plate is parallel to the upper side face of the vertical supporting plate and is connected with the open end of the U-shaped radial supporting plate to form a closed hollow frame, and the lower side face of the vertical supporting plate is connected with the horizontal supporting plate in a vertical relation; the horizontal support plate is fixedly connected with the test bed, the inverter gear box is installed in the closed hollow frame, the axial displacement of the inverter gear box is limited through the axial pressing plate, the inverter gear box is parallel to the horizontal radius of an engine and is adjusted in position and fixed in two vertical directions through the U-shaped radial support plate and the long through holes in the vertical support plate respectively, the spline housing is meshed with a rocking handle spline shaft on the accessory gearbox, and meanwhile, the input gear shaft of the inverter gear box and the rocking handle spline shaft are ensured to be in a good centering state.
Further, in the step (4), when the eddy current sensor is selected, the physical mark is to form a key slot on the output gear shaft; when the photoelectric sensor is selected, the physical mark is to stick a reflecting sheet on the output gear shaft.
Has the advantages that:
1) the mechanical parts related to the method of the invention have simple assembly relation, light weight, small size, high reliability and convenient installation and disassembly;
2) the method does not damage or change the original structure of the aircraft engine, and does not cause any influence on the test run of the engine;
3) according to the inversion gearbox related to the method, only random system errors exist in a gear transmission system, the system errors can be controlled through factors such as machining precision, and accumulated errors cannot be brought to vibration phase measurement.
In conclusion, the method breaks through the bottleneck existing in the existing aeroengine rotor vibration phase measurement, can provide important basis for the analysis and diagnosis of aeroengine rotor faults, can particularly provide direct guidance for the dynamic balance of the aeroengine on the wing, and has great application value.
Drawings
Fig. 1 is a schematic view of an internal rotor-casing structure of a current aircraft engine.
FIG. 2 is a schematic view of the assembly relationship between the inverter gearbox and the aircraft engine.
FIG. 3 is a schematic structural diagram of the inverter gearbox in the embodiment.
FIG. 4 is a schematic structural diagram of a gear pair inside the inverter gearbox in the embodiment.
FIG. 5 is a front view of the mounting assembly and the inverter gearbox of the embodiment after being assembled.
FIG. 6 is a top view of the mounting assembly and the inverter gearbox of the embodiment after assembly.
Fig. 7 is a schematic structural view of the mounting assembly in the embodiment.
FIG. 8 is a schematic structural view of the spline housing in the embodiment.
Fig. 9 is a schematic view of the assembly of the photoelectric sensor and the reflector on the output gear shaft in the embodiment.
FIG. 10 is a schematic structural diagram of a lubrication system of the inverter gearbox in the embodiment.
Wherein, 1-low pressure rotor; 2-accessory case gear box; 3-central bevel gear pair; 4-high pressure moving blades; 5-a high-pressure rotor; 6-a high-pressure compressor duct; 7-a high pressure turbine duct; 8-a combustion chamber; 9-rocking handle spline shaft; 10-rocking handle insertion hole; 11-a low-pressure compressor duct; 12-low pressure moving blades; 13-input gear shaft; 14-a box body; 15-output gear shaft; 16-spline housing; 17-gear pair I; 18-gear pair II; 19-gear pair iii; a 20-U shaped radial support plate; 21-vertical support plate; 22-axial platen; 23-a radial platen; 24-long through holes; 25-a horizontal support plate; 26-clamp I; 27-clamp II; 28-pin; 29-a reflective sheet; 30-diffuse reflection of light; 31-a photosensor; 32-a throttle valve; 33-a heat exchanger; 34-a pump; 35-an oil tank; 36-pipeline.
Detailed Description
The invention is further described with reference to the following figures and detailed description.
Example 1
(1) Designing and processing inverter gear box
Under the premise of not changing the accurate transmission ratio of a transmission gear train between an internal rotor of the aircraft engine and a corresponding rocking handle spline shaft 9 in an accessory case gear box 2, carrying out equivalent reverse reduction on a central bevel gear and the gear train in the accessory case gear box 2, and reducing a plurality of pairs of complex gear pair transmission systems between the rotor and the rocking handle spline shaft 9 to three pairs of gear pairs, wherein the number of pairs of reduced gear pairs is the number of pairs of gear pairs in an inverse gear box, namely a gear pair I17, a gear pair II 18 and a gear pair III 19 marked in figure 4, so as to realize the inversion of the internal transmission relationship of the accessory case gear 2;
as shown in fig. 3 and 4, the inverter gearbox includes a casing 14, an input gear shaft 13, an output gear shaft 15, a transmission gear shaft, rolling bearings and spline housings 16, the rolling bearings are respectively matched with the input gear shaft 13, the transmission gear shaft and the output gear shaft 15, the input gear shaft 13, the transmission gear shaft and the output gear shaft 15 are meshed in sequence, the input gear shaft 13 and the output gear shaft 15 are located outside the casing 14, the transmission gear shaft and the rolling bearings are located inside the casing 14, the spline housings 16 are mounted at one end of the input gear shaft 13 through pins 28 (as shown in fig. 8), and the casing 14 is further processed with a lubricating oil inlet and a lubricating oil outlet;
(2) mounting contravariant gear box
As shown in fig. 7, the mounting assembly comprises a clamp i 26, a clamp ii 27, a horizontal support plate 25, a vertical support plate 21, an axial pressure plate 22, a radial pressure plate 23 and a U-shaped radial support plate 20; the upper side surface of the vertical supporting plate 21 is an inclined surface, the axial pressing plate 22 and the radial pressing plate 23 are respectively provided with an installation through hole, and the end surface of the closed end of the U-shaped radial supporting plate 20 and the lower side surface of the vertical supporting plate 21 are respectively provided with a long through hole 24;
the long through hole 24 on the end face of the closed end of the U-shaped radial support plate 20 and the threaded blind hole at the corresponding position on the upper side of the vertical support plate 21 are installed in a bolt mode, so that two side faces of the U-shaped radial support plate 20 are perpendicular to the upper side face of the vertical support plate 21; the axial pressure plate 22 is perpendicular to the upper side surface of the vertical support plate 21 and is installed in a bolt connection mode with a threaded blind hole at a position corresponding to the U-shaped radial support plate 20; the radial pressing plate 23 is parallel to the upper side surface of the vertical supporting plate 21, and a threaded blind hole at a position corresponding to the open end of the U-shaped radial supporting plate 20 is installed in a bolt connection mode, and the radial pressing plate 23 and the U-shaped radial supporting plate 20 form a closed rectangular hollow frame; the long through hole 24 on the lower side surface of the vertical support plate 21 and the threaded blind hole at the corresponding position on the upper surface of the horizontal support plate 25 are installed in a bolt connection mode; the clamp I26 and the clamp II 27 are correspondingly arranged on two opposite side surfaces of the horizontal support plate 25, so that the clamp I26 and the clamp II 27 are perpendicular to the upper surface of the horizontal support plate 25;
as shown in fig. 5 and 6, the mounting assembly is connected with the test bed through a hoop i 26 and a hoop ii 27, the inverter gear box is mounted in a rectangular hollow frame, the inverter gear box is limited in axial displacement through an axial pressing plate 22, and is adjusted and fixed in two directions parallel to and perpendicular to the horizontal radius of the engine by changing the relative positions of a long through hole 24 on a U-shaped radial supporting plate 20 and a vertical supporting plate 21 and a threaded blind hole where a connecting bolt is located, so that the spline housing 16 is meshed with the rocking handle spline shaft 9 on the accessory case gear box 2 (as shown in fig. 2), and the input gear shaft 13 of the inverter gear box and the rocking handle spline shaft 9 are ensured to be in a good centering state; after an input gear shaft 13 of the inverter gear box is connected with a rocking handle spline shaft 9 through a spline housing 16, when a rotor inside an engine rotates, the rocking handle spline shaft 9 can drive a gear mechanism in the inverter gear box, so that an output gear shaft 15 of the inverter gear box and the rotor rotate synchronously at the same rotating speed, and then the vibration phase is measured on the output gear shaft 15 of the inverter gear box, so that the extraction of the vibration phase of the vibrator can be realized;
(3) build lubricating system of contravariant gear box
According to the actual operation rotating speed range of an engine rotor, selecting lubricating oil with an applicable model, combining a pump 34, an oil tank 35 filled with the lubricating oil, a pipeline (rubber hose) 36, a heat exchanger 33 and a throttle valve 32 according to the actual situation of a test bed, and connecting the combination to a lubricating oil inlet and a lubricating oil outlet on an inverter gearbox, as shown in fig. 10, a lubricating system for building the inverter gearbox can lubricate and cool gears and rolling bearing assemblies in the inverter gearbox, so that the parts are prevented from being damaged due to serious abrasion, gluing and the like;
(4) rotor vibration phase measurement
A reflector 29 is adhered to the output gear shaft 15 of the inverter gear box, the position where the reflector 29 is adhered is used as a '0 phase' reference point of rotor vibration, a photoelectric sensor 31 is opposite to the reflector 29 and is in a triggered state (shown in figure 9), and a vibration sensor is arranged on the outer surface of a rotor case;
then keeping the rotor in a static state, enabling a hole detector to penetrate through a hole detecting hole in the rotor casing, and recording the number of the blade on the blade disc corresponding to the hole detecting hole (the number of the blade is marked in sequence from 1, and the marking sequence of the number of the blade is consistent with the rotation direction of the rotor);
then the test bed is operated, the rotor is stabilized for 1min every 1000rpm in the process of rising from 3000rpm to 8000rpm, the vibration signal and the key phase signal are synchronously collected, and the vibration phase without the uniform reference is firstly calculated by utilizing the waveform of the vibration signal and the pulse square wave of the key phase signal, as shown in table 1;
TABLE 1
| Rotational speed (rpm) | 3000 | 4000 | 5000 | 6000 | 7000 | 8000 |
| Phase (°) | 26 | 73 | 54 | 159 | 237 | 124 |
Finally, converting according to the following formula to obtain the vibration phase of the rotor relative to a unified reference (taking the vibration phase of the initial position of the No. 1 blade on the stage blade disc corresponding to the hole probing hole as a reference);
in the formula, F is a vibration phase with respect to a uniform reference, F' is a vibration phase without a uniform reference, N is a number of blades on the disk corresponding to the hole probing hole (the number of the blade is 21), Z is a total number of blades on the disk corresponding to the hole probing hole (the total number of the blades on the disk is 90), and the calculation results are shown in table 2.
TABLE 2
| Rotational speed (rpm) | 3000 | 4000 | 5000 | 6000 | 7000 | 8000 |
| Phase (°) | 302 | 349 | 330 | 75 | 153 | 40 |
In summary, the above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (6)
1. A rotor vibration phase measuring and calculating method for an aircraft engine test bed is characterized by comprising the following steps: the method comprises the following steps:
step one, designing and processing an inverter gear box
On the premise of not changing the accurate transmission ratio of a transmission gear train between a rotor inside the aircraft engine and a corresponding rocking handle spline shaft (9), carrying out equivalent reverse reduction on the transmission gear train between the rotor and the rocking handle spline shaft (9), wherein the reduced number of pairs of gears is the number of pairs of gears in the reverse gearbox;
a lubricating oil inlet and a lubricating oil outlet are also formed in the inverter gear box;
step two, mounting the inverter gear box
The inverter gear box is installed on the test bed through the installation component, the installation component limits axial displacement of the inverter gear box and adjusts and fixes the position of the inverter gear box in two directions which are parallel to and vertical to the horizontal radius of the engine, so that the input end of a gear train in the inverter gear box is meshed with the rocking handle spline shaft (9), and meanwhile, the centering state of the input end of the gear train in the inverter gear box and the rocking handle spline shaft (9) is ensured; wherein the axial direction is consistent with the axial direction of the input end of the gear train in the inverse gearbox;
step three, building a lubricating system of the inverter gear box
Combining a pump (34), an oil tank (35), a pipeline (36), a heat exchanger (33) and a throttle valve (32) according to the actual situation of a test bed, and connecting the pump, the oil tank, the pipeline (36), the heat exchanger (33) and the throttle valve (32) into a lubricating oil inlet and a lubricating oil outlet on an inverter gearbox to build a lubricating system of the inverter gearbox;
step four, measuring the vibration phase of the rotor
The vibration phase of the output end of the gear train in the inverter gear box is measured, when the rotor in the engine rotates, the rocking handle spline shaft (9) can drive the gear train in the inverter gear box, so that the output end of the gear train in the inverter gear box and the rotor rotate at the same rotating speed synchronously, and the vibration phase is measured at the output end of the gear train in the inverter gear box, namely the vibration phase of the vibrator is measured.
2. The rotor vibration phase estimation method for an aircraft engine test stand according to claim 1, characterized in that: the inversion gearbox comprises a box body (14), an input gear shaft (13), an output gear shaft (15), more than one transmission gear shaft, rolling bearings and a spline housing (16), wherein the rolling bearings are respectively matched with the input gear shaft (13), the more than one transmission gear shaft and the output gear shaft (15), the input gear shaft (13), the more than one transmission gear shaft and the output gear shaft (15) are sequentially meshed, the input gear shaft (13) and the output gear shaft (15) are positioned outside the box body (14), the more than one transmission gear shaft and the rolling bearings are positioned in the box body (14), the spline housing (16) is fixedly installed at one end of the input gear shaft (13), and a lubricating oil inlet and a lubricating oil outlet are further processed on the box body (14);
the spline sleeve (16) on the input gear shaft (13) is meshed with the rocking handle spline shaft (9), the input gear shaft (13) and the rocking handle spline shaft (9) keep a centering state, and the output gear shaft (15) and the rotor synchronously rotate at equal rotating speed through the rocking handle spline shaft (9).
3. The rotor vibration phase estimation method for an aircraft engine test stand according to claim 1, characterized in that: the mounting assembly comprises a horizontal support plate (25), a vertical support plate (21), an axial pressing plate (22), a radial pressing plate (23) and a U-shaped radial support plate (20); wherein, the upper side surface of the vertical supporting plate (21) is an inclined surface, and the end surface of the closed end of the U-shaped radial supporting plate (20) and the lower side surface of the vertical supporting plate (21) are respectively provided with a long through hole (24);
the end face of the closed end of the U-shaped radial support plate (20) is connected with the upper side of the vertical support plate (21), the axial pressing plate (22) is perpendicular to the upper side of the vertical support plate (21) and is connected with the U-shaped radial support plate (20), the radial pressing plate (23) is parallel to the upper side of the vertical support plate (21) and is connected with the open end of the U-shaped radial support plate (20) to form a closed hollow frame, and the lower side of the vertical support plate (21) is connected with the horizontal support plate (25) in a perpendicular relation; horizontal support plate (25) and test bed fixed connection, the contravariant gear box is installed in closed hollow frame, carry out axial displacement restriction to the contravariant gear box through axial clamp plate (22), and parallel with the horizontal radius of engine, the two perpendicular directions carry out position control and fix through long through-hole (24) on U type radial support plate (20) and the vertical support plate (21) respectively to the contravariant gear box, make the input of gear train in the contravariant gear box mesh with rocking handle integral key shaft (9), ensure the centering state of the input of gear train in the contravariant gear box and rocking handle integral key shaft (9) simultaneously.
4. The rotor vibration phase estimation method for an aircraft engine test stand according to claim 1, characterized in that: the specific steps of the rotor vibration phase measurement are as follows,
making a physical mark capable of triggering level conversion of a sensor at the output end of a gear system in an inverter gearbox, taking the physical mark as a '0 phase' reference point of rotor vibration, enabling the sensor to be in a triggered state, and meanwhile, installing a vibration sensor on the outer surface of a rotor casing;
firstly, keeping the rotor in a static state, enabling a hole detector to penetrate through a hole detecting hole in a rotor casing, and recording the number of a blade on a blade disc corresponding to the hole detecting hole;
then synchronously collecting vibration signals and key phase signals when the test bed runs, firstly calculating vibration phases which are not uniformly based according to the collected signals, then converting according to the following formula to obtain the vibration phases of the rotor relative to the uniform reference,
in the formula, F is a vibration phase relative to a uniform reference, F' is a vibration phase without the uniform reference, N is a blade number on a blade disc corresponding to a hole probing hole, and Z is the total number of blades of the blade disc corresponding to the hole probing hole; the blade numbers are marked in sequence from 1, the marking sequence of the blade numbers is consistent with the rotation direction of the rotor, and the vibration phase of the starting position of the blade number 1 on the blade disc corresponding to the hole probing hole is used as a reference.
5. The rotor vibration phase estimation method for an aircraft engine test stand according to claim 4, characterized in that: when the sensor is an eddy current sensor, the physical mark is that a key groove is formed on the output gear shaft (15).
6. The rotor vibration phase estimation method for an aircraft engine test stand according to claim 4, characterized in that: when the sensor selects a photoelectric sensor (31), the physical mark is to paste a reflective sheet (29) on the output gear shaft (15).
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113294512A (en) * | 2021-06-15 | 2021-08-24 | 中国航发沈阳发动机研究所 | Aero-engine central transmission structure adopting face gear for power splitting |
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| 马振涛: "往复压缩机无级气量调节关键技术与发动机试验台建设研究", 《中国优秀硕士学位论文全文数据库工程科技Ⅱ辑》 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113294512A (en) * | 2021-06-15 | 2021-08-24 | 中国航发沈阳发动机研究所 | Aero-engine central transmission structure adopting face gear for power splitting |
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